<html><head>
<title> FFA-W3-211, Fixed Transition </title></head>

<body BGPROPERTIES="FIXED" face="ARIAL" size="3" text="#000000"
bgcolor="#ffffff"  link="#ff0000" vlink="#aaaaff" alink="#FF00ff">

<br>
<center>
<H1>FFA-W3-211 AIRFOIL, Fixed Transition</H1>
</center>

<P><hr size=3 noshade></P>
<br>

Reynolds number = 1.8 x 10^6 <br><br>

Fixed transition at 5% chordwise <br><br>

Manufactured and equipped at FFA (The Aeronautical Research Institute
of Sweden) and measured at KTH, Royal Institute of
Technology, Stockholm (see
<A HREF="./../../HTML/biblio.htm#Bjorck">Bj&ouml;rck (1996)</A>) <br><br>

More details on computations and experimental facilities can be found in
the <A HREF="./../../HTML/report.htm"><font color="#006699">Wind Turbine
Airfoil Catalogue</font></A>.


<br><br><br>
<HR width=50% size=5>
<br><br>

<H1>DATA AVAILABLE:</H1><p><p>

- <A HREF="./../prof.dat"> Airfoil shape </A><p>

<font size=+3> Experiments:<br> </font>
- <A HREF="./cldm.exp"> Lift, Drag and Moment Coefficients </A><p>

- <A HREF="./cp_07.99.exp"> Pressure Distribution - Angle of Attack = 07.99 deg. </A><br>
- <A HREF="./cp_10.47.exp"> Pressure Distribution - Angle of Attack = 10.47 deg. </A><br>
- <A HREF="./cp_14.98.exp"> Pressure Distribution - Angle of Attack = 14.98 deg. </A><br>
- <A HREF="./cp_20.33.exp"> Pressure Distribution - Angle of Attack = 20.33 deg. </A><p>

<font size=+3> XFOIL Computations:<br> </font>
- <A HREF="./cldm.xf"> Lift, Drag and Moment Coefficients </A><p>
- <A HREF="./cfp_05.10.xf"> Skin Friction and Pressure Distributions - Angle of Attack = 05.10 deg. </A><br>
- <A HREF="./cfp_07.99.xf"> Skin Friction and Pressure Distributions - Angle of Attack = 07.99 deg. </A><br>
- <A HREF="./cfp_10.47.xf"> Skin Friction and Pressure Distributions - Angle of Attack = 10.47 deg. </A><br>
- <A HREF="./cfp_14.98.xf"> Skin Friction and Pressure Distributions - Angle of Attack = 14.98 deg. </A><br>
- <A HREF="./cfp_17.00.xf"> Skin Friction and Pressure Distributions - Angle of Attack = 17.00 deg. </A><br>
- <A HREF="./cfp_20.33.xf"> Skin Friction and Pressure Distributions - Angle of Attack = 20.33 deg. </A><p>

<font size=+3> EllipSys2D Computations: </font><p>
<font size=+2><em>* Fixed transition:</em><br> </font>
- <A HREF="./cldm.ellipsys"> Lift, Drag and Moment Coefficients </A><p>
- <A HREF="./cp_05.10.ellipsys"> Pressure Distribution - Angle of Attack = 05.10 deg. </A><br>
- <A HREF="./cp_07.99.ellipsys"> Pressure Distribution - Angle of Attack = 07.99 deg. </A><br>
- <A HREF="./cp_10.47.ellipsys"> Pressure Distribution - Angle of Attack = 10.47 deg. </A><br>
- <A HREF="./cp_14.98.ellipsys"> Pressure Distribution - Angle of Attack = 14.98 deg. </A><br>
- <A HREF="./cp_17.00.ellipsys"> Pressure Distribution - Angle of Attack = 17.00 deg. </A><br>
- <A HREF="./cp_20.33.ellipsys"> Pressure Distribution - Angle of Attack = 20.33 deg. </A><p>

- <A HREF="./cf_05.10.ellipsys"> Skin Friction Distribution - Angle of Attack = 05.10 deg. </A> <br>
- <A HREF="./cf_07.99.ellipsys"> Skin Friction Distribution - Angle of Attack = 07.99 deg. </A> <br>
- <A HREF="./cf_10.47.ellipsys"> Skin Friction Distribution - Angle of Attack = 10.47 deg. </A> <br>
- <A HREF="./cf_14.98.ellipsys"> Skin Friction Distribution - Angle of Attack = 14.98 deg. </A> <br>
- <A HREF="./cf_17.00.ellipsys"> Skin Friction Distribution - Angle of Attack = 17.00 deg. </A> <br>
- <A HREF="./cf_20.33.ellipsys"> Skin Friction Distribution - Angle of Attack = 20.33 deg. </A>


<br><br><br>
<HR width=50% size=5>
<br><br>

<H1>FIGURES AVAILABLE: (PostScript files)</H1><p><p>

- <A HREF="./../profile.ps"> Airfoil shape </A><p>

- <A HREF="./PS/cl.ps"> Lift Coefficient </A><br>
- <A HREF="./PS/cd.ps"> Drag Coefficient </A><br>
- <A HREF="./PS/cm.ps"> Moment Coefficient </A><p>

- <A HREF="./PS/cp_a05.10.ps"> Pressure Distribution - Angle of Attack = 05.10 deg. </A><br>
- <A HREF="./PS/cp_a07.99.ps"> Pressure Distribution - Angle of Attack = 07.99 deg. </A><br>
- <A HREF="./PS/cp_a10.47.ps"> Pressure Distribution - Angle of Attack = 10.47 deg. </A><br>
- <A HREF="./PS/cp_a14.98.ps"> Pressure Distribution - Angle of Attack = 14.98 deg. </A><br>
- <A HREF="./PS/cp_a17.00.ps"> Pressure Distribution - Angle of Attack = 17.00 deg. </A><br>
- <A HREF="./PS/cp_a20.33.ps"> Pressure Distribution - Angle of Attack = 20.33 deg. </A><p>

- <A HREF="./PS/cf_a05.10.ps"> Skin Friction Distribution - Angle of Attack = 05.10 deg. </A><br>
- <A HREF="./PS/cf_a07.99.ps"> Skin Friction Distribution - Angle of Attack = 07.99 deg. </A><br>
- <A HREF="./PS/cf_a10.47.ps"> Skin Friction Distribution - Angle of Attack = 10.47 deg. </A><br>
- <A HREF="./PS/cf_a14.98.ps"> Skin Friction Distribution - Angle of Attack = 14.98 deg. </A><br>
- <A HREF="./PS/cf_a17.00.ps"> Skin Friction Distribution - Angle of Attack = 17.00 deg. </A><br>
- <A HREF="./PS/cf_a20.33.ps"> Skin Friction Distribution - Angle of Attack = 20.33 deg. </A><p>



<br><br>
<HR width=50% size=5>
<br><br>

<TABLE border=0 width=100%>
<TR>
<TD align=left> <A HREF="./../../HTML/a_index.htm"><B><font color="#006699">
Back to airfoils index</font><B></A></TD>
<TD align=right><A HREF="./../../HTML/main.htm"><B><font color="#006699">
Back to airfoil catalogue home page</font></B></A></TD>
</TR>
</TABLE>
<br><br>

</BODY>
</html>
